The new expression includes effects from pitching, plunging, and surging motions, as well as spatial nonuniformity of the flow. This paper derives a new expression for and effective angle of attack that relaxes the small-angle and small-camber-slope assumptions. The existing expression for effective angle of attack depends on attached-flow, thin-airfoil, small-angle, and small-camber-slope assumptions. For a maneuvering airfoil, the instantaneous effective angle of attack is a virtual angle that corresponds to the equivalent lift based on a steady, lift versus angle-of-attack curve. The effective angle of attack of an airfoil is a composite mathematical expression from quasi-steady thin-airfoil theory that combines the geometric contribution to the angle of attack with pitching and plunging effects.
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